EP1046783B1 - Turbine blade units - Google Patents
Turbine blade units Download PDFInfo
- Publication number
- EP1046783B1 EP1046783B1 EP00116388A EP00116388A EP1046783B1 EP 1046783 B1 EP1046783 B1 EP 1046783B1 EP 00116388 A EP00116388 A EP 00116388A EP 00116388 A EP00116388 A EP 00116388A EP 1046783 B1 EP1046783 B1 EP 1046783B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blades
- blade
- turbine
- root
- tip
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/145—Means for influencing boundary layers or secondary circulations
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/10—Manufacture by removing material
- F05D2230/12—Manufacture by removing material by spark erosion methods
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/16—Two-dimensional parabolic
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S415/00—Rotary kinetic fluid motors or pumps
- Y10S415/914—Device to control boundary layer
Definitions
- Patent Application No. EP95305720.5 is directed to a turbine blade having at least approximately constant cross-section between root and tip and in which the aerofoil sections are rotated about the trailing edge so as to provide a substantially symmetrical convex curvature in the radial direction on the pressure face of the blade between the root and tip.
- the present invention relates to a turbine having a ring of turbine blades as shown in e.g. the prior art document EP- A- 0 570 106. While the invention is primarily concerned with steam turbines it is also applicable to other turbines and to compressors. The term "turbine” is used in this specification to include machines of this kind having aerofoil blades. It is also primarily concerned with fixed blades in turbines but is not exclusive to them.
- Turbine efficiency is of great importance, particularly in large installations where a fractional increase in efficiency can produce very large cost savings. A considerable amount of money and effort is continually expended therefore on research into the blade design, for example, this being a critical component.
- the conventional blade has been of aerofoil cross-section, the (fixed) blade extending radially between inner and outer end blocks, and the blade being of prismatic form, i.e. generated by a line moving parallel to itself and intersecting an aerofoil section.
- the orientations of both fixed and moving blades about their respective blade axes has also been standardised for this prismatic blade design, this orientation being defined by the blade stagger angle between the turbine axial direction and a line tangential to the blade leading edge and trailing edge circles on the pressure face of the aerofoil blade.
- a known improvement in the performance of the prismatic blade in the turbine is achieved by imposing a 'lean' on the blade, i.e. tilting it about its root in a circumferential plane i.e. one transverse, or perpendicular, to the turbine axis.
- This 'lean' produces a variation in the mass flow at outlet of the blade from the root to the tip.
- the radially inner and outer ends of the blade are referred to as the root and the tip despite the fact that both root and 'tip' are terminated by the end walls of the supporting rings 21 and 22 shown in the accompanying Figure 1. Since the circumferential spacing of the blades (i.e.
- the blade outlet angle ⁇ is illustrated in Figures 3(a) and 3(b) of the accompanying drawings and is defined as sin -1 (throat/blade pitch).
- the throat is the shortest width in the blade passages. It normally extends from the pressure surface of a blade at the trailing edge and is orthogonal to the suction surface of the adjacent blade.
- the stagger angle is the angle between the axis of the turbine and the tangent line touching the leading and trailing circles of the aerofoil section.
- the blade chord length is the overall extent of the blade along the stagger angle tangent line.
- a turbine having a ring of aerofoil blades mounted between inner and outer end blocks, each working fluid path between adjacent blades being closed in cross-section by the end walls formed by said end blocks, wherein the blades and their associated end blocks are formed integrally and machined to provide fillets between the blade aerofoil surfaces and the end walls, said fillets having a radius in the range 0.15 to 0.3 of a throat dimension between adjacent blades, said throat dimension being the shortest line that extends perpendicularly from the suction face of a blade to meet the pressure face of an adjacent blade, and wherein said fillets at the tip of the blades have a radius determined by said throat dimension at the tip of the blades and said fillets at the root of the blades have a radius determined by said throat dimension at the root of the blades, or said fillets at both the tip and the root of the blades have a radius determined by a mean value of said throat dimension at the root and tip of the blades
- the multiplying factor of the fillet radius preferably lies in the range 0.2 to 0.25, or more preferably has the approximate value 0.23.
- the fillets may be extended behind respective trailing edges of said blades, the fillets in this region being of concave form and merging into their respective end-walls at a point downstream of said respective trailing edges.
- Each of the blades may be of at least approximately constant aerofoil cross-section from its root at the radially inner end to its tip at the radially outer end, and be substantially symmetrically curved between the root and the tip so that the pressure face of the aerofoil blade is convex in the radial direction between root and tip.
- the aerofoil sections at the root and tip of the blade may be rotated in their own plane relative to the mid-height section by an angle preferably within the range 5° ⁇ 2°, and preferably again, within the range 5° ⁇ 1 °.
- the aerofoil sections of the blade preferably lie on a parabolic curve between the root and the tip.
- the trailing edge of the blade is preferably straight from root to tip, the convex curvature of the blade pressure face in the radial direction being achieved by rotational displacement of the aerofoil sections about the straight trailing edge.
- the ratio of the throat between adjacent fixed blades to the pitch of the blades gives the sine of an outlet angle for the blades which is preferably in the range 7° to 11° at the root of the blades, and more preferably in the range 8° to 10°.
- the setting angle of the mid-height section of the fixed blades is preferably such, in combination with the root outlet angle, as to provide a total passage throat area equal to that of a turbine having prismatic blades of the same stagger angle.
- the outlet angle at the root of the blades may be constant throughout the series of stages and the setting angle for the blade aerofoil sections at the radial mid-height of the blades may be such as to maintain a predetermined throat area for the blades of each stage.
- This predetermined throat area may be the throat area provided by prismatic blades in the corresponding stage of an otherwise similar conventional turbine.
- Figure 1 a diagrammatic axial section view of a conventional 'disc and diaphragm' high/intermediate pressure steam turbine stage.
- the direction of flow F of the working fluid, steam is approximately parallel to the turbine rotor axis A.
- the rotor 10 has, for each stage, a disc 11 to which is secured a set or row of circumferentially aligned and spaced apart moving blades 12, the blades 12 having a shroud 13 attached to their radially outer ends. Energy in the steam flowing in the direction F from the front to the rear of the turbine is converted into mechanical energy in the rotor 12.
- a fixed blade assembly precedes the set of moving blades 12 and is secured to the turbine inner casing 20.
- This fixed blade assembly comprises a radially inner ring 21, a radially outer ring 22 and a row of circumferentially aligned and spaced apart fixed blades 23, each blade 23 being secured at an inner end to the inner ring 21 and at an outer end to the outer ring 22, and each blade having a leading edge 24 facing the flow and a trailing edge 25.
- the assembly of blades 23 with the inner and outer rings 21, 22 is known as a diaphragm.
- the disc and diaphragm stage as shown in Figure 1 is of the type in which the area between the inner and outer rings 21, 22 orthogonal to the turbine axis A is larger at the fixed blade trailing edges 25 than at the blade leading edges 24.
- the surfaces, i.e. the end walls, of the rings (or end blocks) 21, 22 to which the blades 23 are secured have a frusto-conical shape diverging from the turbine axis A in the direction F from the leading 24 to the trailing 25 edges of the blades 23.
- FIG 2 there is shown a rear view of part of a fixed blade assembly which is of the type shown in Figure 1.
- the fixed blades 23 shown in Figure 2 are of the conventional prismatic kind, that is, they are each straight, i.e. designed such that the notional aerofoil sections of the blade, each considered orthogonal to a radial line from the turbine axis, have the same shape from the blade inner end to the blade outer end are untwisted from the root end to the tip end and are stacked with the leading edge 24 and the trailing edge 25 each on a straight line.
- Each blade 23 has a concave pressure side 26 and a convex suction side 27.
- this illustrates, in a radial plan view, the orientation of the fixed blades 23 and 29 relative to the turbine axis A and the transverse (i.e., tangential or circumferential) plane T containing the fixed blade ring and to which the axis A is perpendicular.
- the blade aerofoil section is based on a small trailing edge circle 15 and a larger leading edge circle 17.
- the tangent line 19 to these two circles is at an angle ⁇ , the stagger angle, from the axis A direction.
- Figure 4 shows a blade which is shaped in accordance with the principles of the invention. It has a straight trailing edge 25 like the conventional prismatic blade but the remainder of the blade, and in particular the leading edge 24, is not straight but is curved in a manner such that the pressure face of the blade is convex in the radial direction between root and tip, that is, in a plane which is transverse to the general steam flow direction between the blades.
- One such plane 31 is indicated in Figure 4, the convex curvature in this plane on the pressure face 26 being obscured but conforming to that at the leading edge 24.
- FIG. 5 This curvature is illustrated in Figure 5 by the change in the setting angle of the various aerofoil sections 33 of Figure 4 from the root 35 to the tip 37 of the blade.
- the individual aerofoil sections 33 may be considered as being rotated in their own planes about the trailing edge 25 by a setting angle which is positive in the central part of the radial height, and negative in the root and tip portions.
- 'Positive' is taken to be a rotation toward the pressure face 26 and negative toward the suction face 27.
- a zero setting angle occurs at about one-fifth and four-fifths of the radial blade height where the aerofoil section has the same stagger angle, i.e. the same orientation relative to the turbine axis, as a conventional prismatic blade in an otherwise similar conventional turbine.
- This 'conventional' stagger angle is assumed to be 48.5°.
- the setting angle varies from about minus 2.5° at the root and tip to plus 2.5° at the centre of the radial height. This is a preferred arrangement where the conventional, i.e. reference, stagger angle is 48.5°. However, variations in the setting angle 5° difference will still produce efficiency benefits if only to a lesser extent. It is envisaged that a variation of ⁇ 2°on the 5° difference will still be beneficial, i.e. a range of setting angle differences from 3° between root/tip and centre height, to 7° between root/tip and centre height. It is preferred however to limit the variation to ⁇ 1°, i.e. differences from 4° to 6°.
- the variation of setting angle throughout the height of the blade is preferably parabolic, as illustrated in Figure 5.
- the outlet angle increases almost linearly from about 13° at the blade root to about 15° at the tip.
- This increase in the opening corresponds simply to the increase in the blade pitch with increasing radius.
- the outlet angle varies from about 9.6° at the root to about 15.6° at the mid-height and back to 12° at the tip.
- This asymmetry similarly derives from the increase in the blade pitch with radius since the throat moves upstream (on the suction surface) with increase of pitch and since the throat increases faster than the pitch the outlet angle increases with pitch and therefore with radius.
- This difference of outlet angle between tip and root is despite the setting angle being the same at tip and root.
- the effect of the curved blade is to reduce the flow through both of the high loss regions near the root and tip end walls and increase the flow through the more efficient mid-height region.
- the best prismatic design of which the Applicants are aware is one having a straight negative lean of 8° i.e., in which the fixed blades lean in the transverse plane in a direction toward the suction face at an angle of 8° to the radius through their root.
- the curved blade of the present invention when tested in a two-stage air turbine has shown an efficiency gain of 0.8% compared to this 'best' conventional design.
- a turbine according to the present invention concerns the construction of fixed blades between their end blocks.
- the blades are machined or cast in groups integrally with their end blocks which are sections of the rings 21 and 22 ( Figures 1 and 2).
- the blade units are then machined to provide the necessary accurate dimensioning and surface finish.
- Figure 7 is a diagram of a cross-section of part of the throat passage between two fixed blades. It has been found that the radius of the fillet between the end blocks 21 and 22 has a significant effect on the stage efficiency. The optimum fillet radius has been found to be in the range 0.15 to 0.3 of the throat dimension with a preferred part of this range being 0.2 to 0.25 and, in particular, 0.23.
- Figure 8a represents an end view of a trailing edge 25 with a conventional fillet between the edge 25 and the end wall 21, and Figure 8b represents the same view but with a "faired-out” fillet.
- Figure 8c A partial side view of Figure 8b is shown in Figure 8c, where the fillet can be clearly seen to disappear to zero at its most downstream point from the trailing edge.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
- The present application is divided out of Patent Application No. EP95305720.5, which is directed to a turbine blade having at least approximately constant cross-section between root and tip and in which the aerofoil sections are rotated about the trailing edge so as to provide a substantially symmetrical convex curvature in the radial direction on the pressure face of the blade between the root and tip.
- The present invention relates to a turbine having a ring of turbine blades as shown in e.g. the prior art document EP- A- 0 570 106. While the invention is primarily concerned with steam turbines it is also applicable to other turbines and to compressors. The term "turbine" is used in this specification to include machines of this kind having aerofoil blades. It is also primarily concerned with fixed blades in turbines but is not exclusive to them.
- Turbine efficiency is of great importance, particularly in large installations where a fractional increase in efficiency can produce very large cost savings. A considerable amount of money and effort is continually expended therefore on research into the blade design, for example, this being a critical component.
- For many years the conventional blade has been of aerofoil cross-section, the (fixed) blade extending radially between inner and outer end blocks, and the blade being of prismatic form, i.e. generated by a line moving parallel to itself and intersecting an aerofoil section. The orientations of both fixed and moving blades about their respective blade axes has also been standardised for this prismatic blade design, this orientation being defined by the blade stagger angle between the turbine axial direction and a line tangential to the blade leading edge and trailing edge circles on the pressure face of the aerofoil blade.
- A known improvement in the performance of the prismatic blade in the turbine is achieved by imposing a 'lean' on the blade, i.e. tilting it about its root in a circumferential plane i.e. one transverse, or perpendicular, to the turbine axis. This 'lean' produces a variation in the mass flow at outlet of the blade from the root to the tip. The radially inner and outer ends of the blade are referred to as the root and the tip despite the fact that both root and 'tip' are terminated by the end walls of the supporting
rings - The blade outlet angle α is illustrated in Figures 3(a) and 3(b) of the accompanying drawings and is defined as sin-1 (throat/blade pitch).
- From the same figures the following parameters appear. The throat is the shortest width in the blade passages. It normally extends from the pressure surface of a blade at the trailing edge and is orthogonal to the suction surface of the adjacent blade.
- The stagger angle is the angle between the axis of the turbine and the tangent line touching the leading and trailing circles of the aerofoil section.
- The blade chord length is the overall extent of the blade along the stagger angle tangent line.
- Modifications to the basic prismatic blade design have in the past been proposed. For example, in the Hitachi Review Vol. 27, No. 3 of 1978, twisted and other blade forms were proposed. In what was referred to as the 'controlled vortex nozzle design' there was described a nozzle (i.e. fixed blade) which conformed to the conventional prismatic blade form for the lower half of its radial height but which had a progressively finer setting angle for the upper half. The setting angle is the angle by which the aerofoil section at any blade height is rotated within its own plane from the normal disposition for a prismatic blade. A fine setting indicates a rotation of the aerofoil section to reduce the throat and thus reduce the outlet angle and a coarse setting a rotation to increase it. Figure 3 of this earlier article illustrates a continuous rotation of the blade section from the root to the tip, the setting angle becoming finer with increased blade height.
- According to the present invention, there is provided a turbine having a ring of aerofoil blades mounted between inner and outer end blocks, each working fluid path between adjacent blades being closed in cross-section by the end walls formed by said end blocks, wherein the blades and their associated end blocks are formed integrally and machined to provide fillets between the blade aerofoil surfaces and the end walls, said fillets having a radius in the range 0.15 to 0.3 of a throat dimension between adjacent blades, said throat dimension being the shortest line that extends perpendicularly from the suction face of a blade to meet the pressure face of an adjacent blade, and wherein
said fillets at the tip of the blades have a radius determined by said throat dimension at the tip of the blades and said fillets at the root of the blades have a radius determined by said throat dimension at the root of the blades, or
said fillets at both the tip and the root of the blades have a radius determined by a mean value of said throat dimension at the root and tip of the blades.. - The multiplying factor of the fillet radius preferably lies in the range 0.2 to 0.25, or more preferably has the approximate value 0.23.
- The fillets may be extended behind respective trailing edges of said blades, the fillets in this region being of concave form and merging into their respective end-walls at a point downstream of said respective trailing edges.
- Each of the blades may be of at least approximately constant aerofoil cross-section from its root at the radially inner end to its tip at the radially outer end, and be substantially symmetrically curved between the root and the tip so that the pressure face of the aerofoil blade is convex in the radial direction between root and tip.
- The aerofoil sections at the root and tip of the blade may be rotated in their own plane relative to the mid-height section by an angle preferably within the range 5° ± 2°, and preferably again, within the range 5° ± 1 °.
- The aerofoil sections of the blade preferably lie on a parabolic curve between the root and the tip.
- The trailing edge of the blade is preferably straight from root to tip, the convex curvature of the blade pressure face in the radial direction being achieved by rotational displacement of the aerofoil sections about the straight trailing edge.
- Where the blades are fixed blades, the ratio of the throat between adjacent fixed blades to the pitch of the blades gives the sine of an outlet angle for the blades which is preferably in the range 7° to 11° at the root of the blades, and more preferably in the
range 8° to 10°. - The setting angle of the mid-height section of the fixed blades is preferably such, in combination with the root outlet angle, as to provide a total passage throat area equal to that of a turbine having prismatic blades of the same stagger angle.
- Where the turbine has a series of stages adapted for decreasing fluid density of the working fluid, the outlet angle at the root of the blades may be constant throughout the series of stages and the setting angle for the blade aerofoil sections at the radial mid-height of the blades may be such as to maintain a predetermined throat area for the blades of each stage. This predetermined throat area may be the throat area provided by prismatic blades in the corresponding stage of an otherwise similar conventional turbine.
- A turbine blade, being the subject-matter of parent patent application EP95305720.5, and its incorporation in a steam turbine, will now be described, by way of example, with reference to the accompanying drawings, in which:
- Figure 1 is a diagrammatic sectional view on the axis of a steam turbine showing a conventional 'disc and diaphragm' high/intermediate pressure steam turbine stage including an assembly of fixed blades;
- Figure 2 is a perspective view of two such conventional blades in the fixed blade diaphragm;
- Figure 3 (a) is a diagrammatic radial view of the blades of Figure 2;
- Figure 3 (b) is a diagram illustrating the outlet angle from the fixed blades;
- Figure 4 is a perspective view of a fixed blade according to the invention. The grid pattern shown on the surface is not of course present in reality but serves to emphasize the curved formation of the blade;
- Figure 5 is a graph of blade section setting angle against height of the section from root to tip of the blade, for conventional prismatic blade and blade according to the invention;
- Figure 6 is a graph of blade outlet angle against section height, again for the two types of blade;
- Figure 7 is a partial cross-section of the throat passage between two blades showing the fillets formed between the two blades and the end block, and
- Figure 8 is a diagram showing a trailing blade edge with a conventional fillet and one with a "faired-out" fillet.
- Referring now to the drawings, there is shown in Figure 1 a diagrammatic axial section view of a conventional 'disc and diaphragm' high/intermediate pressure steam turbine stage. The direction of flow F of the working fluid, steam, is approximately parallel to the turbine rotor axis A. The
rotor 10 has, for each stage, adisc 11 to which is secured a set or row of circumferentially aligned and spaced apart movingblades 12, theblades 12 having ashroud 13 attached to their radially outer ends. Energy in the steam flowing in the direction F from the front to the rear of the turbine is converted into mechanical energy in therotor 12. For each stage, a fixed blade assembly precedes the set of movingblades 12 and is secured to the turbineinner casing 20. This fixed blade assembly comprises a radiallyinner ring 21, a radiallyouter ring 22 and a row of circumferentially aligned and spaced apart fixedblades 23, eachblade 23 being secured at an inner end to theinner ring 21 and at an outer end to theouter ring 22, and each blade having a leadingedge 24 facing the flow and atrailing edge 25. The assembly ofblades 23 with the inner andouter rings outer rings blade trailing edges 25 than at theblade leading edges 24. Furthermore, in the example shown in Figure 1, the surfaces, i.e. the end walls, of the rings (or end blocks) 21, 22 to which theblades 23 are secured have a frusto-conical shape diverging from the turbine axis A in the direction F from the leading 24 to the trailing 25 edges of theblades 23. - Referring now to Figure 2, there is shown a rear view of part of a fixed blade assembly which is of the type shown in Figure 1. The
fixed blades 23 shown in Figure 2 are of the conventional prismatic kind, that is, they are each straight, i.e. designed such that the notional aerofoil sections of the blade, each considered orthogonal to a radial line from the turbine axis, have the same shape from the blade inner end to the blade outer end are untwisted from the root end to the tip end and are stacked with the leadingedge 24 and thetrailing edge 25 each on a straight line. Eachblade 23 has aconcave pressure side 26 and aconvex suction side 27. - Referring to Figure 3(a) this illustrates, in a radial plan view, the orientation of the
fixed blades trailing edge circle 15 and a largerleading edge circle 17. Thetangent line 19 to these two circles is at an angle ψ, the stagger angle, from the axis A direction. - If a perpendicular line is drawn from the
suction face 27 ofblade 23 to meet thepressure face 26 of theadjacent blade 29, and then if the shortest such line is taken, this is the throat dimension t, which occurs in the region of the trailingedge 25 of theblade 29. The ratio of this dimension t to the pitch p of the fixed blades gives the sine of what is known as the outlet angle α. It may be seen that, approximately, this angle is the outlet angle from each blade relative to the transverse plane T. - Figure 4 shows a blade which is shaped in accordance with the principles of the invention. It has a
straight trailing edge 25 like the conventional prismatic blade but the remainder of the blade, and in particular the leadingedge 24, is not straight but is curved in a manner such that the pressure face of the blade is convex in the radial direction between root and tip, that is, in a plane which is transverse to the general steam flow direction between the blades. Onesuch plane 31 is indicated in Figure 4, the convex curvature in this plane on thepressure face 26 being obscured but conforming to that at theleading edge 24. - More specifically this curvature is illustrated in Figure 5 by the change in the setting angle of the
various aerofoil sections 33 of Figure 4 from theroot 35 to thetip 37 of the blade. Theindividual aerofoil sections 33 may be considered as being rotated in their own planes about the trailingedge 25 by a setting angle which is positive in the central part of the radial height, and negative in the root and tip portions. 'Positive' is taken to be a rotation toward thepressure face 26 and negative toward thesuction face 27. - In the particular example of Figure 5, a zero setting angle occurs at about one-fifth and four-fifths of the radial blade height where the aerofoil section has the same stagger angle, i.e. the same orientation relative to the turbine axis, as a conventional prismatic blade in an otherwise similar conventional turbine. This 'conventional' stagger angle is assumed to be 48.5°.
- The setting angle varies from about minus 2.5° at the root and tip to plus 2.5° at the centre of the radial height. This is a preferred arrangement where the conventional, i.e. reference, stagger angle is 48.5°. However, variations in the setting angle 5° difference will still produce efficiency benefits if only to a lesser extent. It is envisaged that a variation of ± 2°on the 5° difference will still be beneficial, i.e. a range of setting angle differences from 3° between root/tip and centre height, to 7° between root/tip and centre height. It is preferred however to limit the variation to ± 1°, i.e. differences from 4° to 6°.
- The variation of setting angle throughout the height of the blade is preferably parabolic, as illustrated in Figure 5.
- It would to some extent be acceptable to skew the aerofoil sections about some other axis than the trailing
edge 25, for example the leadingedge 24 or some intermediate axis. However, the choice of the trailing edge as the rotation axis has several advantages. It keeps the critical inter-space gap between the fixed and downstream moving blades constant. This gap has an important influence upon the unsteady aerodynamic forces on the moving blade and also on the stage efficiency via boundary layer growth on the end walls. Secondly, by building the curvature largely into the leading edge a "compound lean" effect is incorporated into the leading edge area of the blade where secondary flows are generated. These secondary flows comprise vortices in parallel with the main flow the vortices being near the end walls between adjacent fixed blades. By the use of the compound curved blade of the invention, over the inner (i.e. lower) half of the blade height the pressure surface points radially inwards, and over the outer half of the blade height the pressure surface points radially outwards. The body forces exerted on the flow are counteracted by higher static pressures on the end walls. This results in lower velocities near the end walls and hence lower frictional losses. - Referring now to Figure 6, this illustrates the relation between outlet angle α and radial height of the blade section (33 in Figure 4).
- In the conventional, prismatic, case, the outlet angle increases almost linearly from about 13° at the blade root to about 15° at the tip. This increase in the opening corresponds simply to the increase in the blade pitch with increasing radius. In a turbine stage incorporating the fixed blade of this embodiment, and having a form defined by the setting angle graph of Figure 5, the outlet angle varies from about 9.6° at the root to about 15.6° at the mid-height and back to 12° at the tip. This asymmetry similarly derives from the increase in the blade pitch with radius since the throat moves upstream (on the suction surface) with increase of pitch and since the throat increases faster than the pitch the outlet angle increases with pitch and therefore with radius. This difference of outlet angle between tip and root is despite the setting angle being the same at tip and root.
- The effect of the curved blade is to reduce the flow through both of the high loss regions near the root and tip end walls and increase the flow through the more efficient mid-height region.
- The best prismatic design of which the Applicants are aware is one having a straight negative lean of 8° i.e., in which the fixed blades lean in the transverse plane in a direction toward the suction face at an angle of 8° to the radius through their root. The curved blade of the present invention when tested in a two-stage air turbine has shown an efficiency gain of 0.8% compared to this 'best' conventional design.
- It is thought that a benefit arises not only in the fixed blade row but also in the downstream moving blade row, as lower mass flows are passed into the end wall regions where there are high secondary losses.
- Where the concept is applied to a series of stages in a complete high pressure or intermediate pressure cylinder, where the blade height increases as the steam density decreases, the following technique is used:
- (a) the outlet angle of the blade section at the root is maintained at about 9° throughout the stages;
- (b) the same setting angle is used at the tip as for the root, i.e. the blade is symmetrical about the mid-height;
- (c) the setting angle at the mid-height section is chosen to keep the mean throat (over the blade height) the same as for a prismatic blade in the same stage. This keeps the stage reaction at the same level as for the corresponding conventional design.
- (d) a parabolic distribution of setting angle over the blade height is used as for the basic design.
- It may be seen that for a series of stages the blade form is simply stretched radially according to the height of the stage blade.
- While the blade design has been described in relation to the use of 'short height' HP/IP fixed blades in a steam turbine of the low reaction disc and diaphragm type, it is also applicable to other types of axial flow turbine and compressor, and to moving as well as fixed blades.
- A turbine according to the present invention concerns the construction of fixed blades between their end blocks. The blades are machined or cast in groups integrally with their end blocks which are sections of the
rings 21 and 22 (Figures 1 and 2). The blade units are then machined to provide the necessary accurate dimensioning and surface finish. - Figure 7 is a diagram of a cross-section of part of the throat passage between two fixed blades. It has been found that the radius of the fillet between the end blocks 21 and 22 has a significant effect on the stage efficiency. The optimum fillet radius has been found to be in the range 0.15 to 0.3 of the throat dimension with a preferred part of this range being 0.2 to 0.25 and, in particular, 0.23.
-
- However, the use of two different values of radius requires the use of different cutting tools during the manufacturing process, and it is possible to compromise by having just one radius value which is an average of the above values, i.e.:
Tests in a two-stage air turbine using the above "average" fillet radius in conjunction with the described "controlled flow" blade design show a stage efficiency gain of around 1.2% relative to the best conventional design with prismatic fixed blades (set with -5 ° straight "lean" of the trailing edges). - It is also advantageous, in order to reduce blockage effects, to "fair out" the fillet downstream of the trailing edge of the blade. This is shown in Figure 8, where Figure 8a represents an end view of a trailing
edge 25 with a conventional fillet between theedge 25 and theend wall 21, and Figure 8b represents the same view but with a "faired-out" fillet. A partial side view of Figure 8b is shown in Figure 8c, where the fillet can be clearly seen to disappear to zero at its most downstream point from the trailing edge.
Claims (16)
- A turbine having a ring of aerofoil blades (23, 29) mounted between inner (21) and outer (22) end blocks, each working fluid path between adjacent blades being closed in cross-section by the end walls formed by said end blocks, wherein the blades and their associated end blocks are formed integrally and machined to provide fillets between the blade aerofoil surfaces and the end walls, characterised in that
said fillets have a radius (rF) in the range 0.15 to 0.3 of a throat dimension (t) between adjacent blades (23, 29), said throat dimension being the shortest line that extends perpendicularly from the suction face (27) of a blade to meet the pressure face (26) of an adjacent blade, and wherein
said fillets at the tip of the blades have a radius determined by said throat dimension at the tip of the blades and said fillets at the root of the blades have a radius determined by said throat dimension at the root of the blades, or
said fillets at both the tip and the root of the blades have a radius determined by a mean value of said throat dimension at the root and tip of the blades. - A turbine according to Claim 1, wherein the multiplying factor of the fillet radius lies in the range 0.2 to 0.25.
- A turbine according to Claim 1, wherein the multiplying factor of the fillet radius is approximately 0.23.
- A turbine according to any one of the preceding claims, wherein said fillets are extended behind respective trailing edges of said blades, the fillets in this region being of concave form and merging into their respective end-walls at a point downstream of said respective trailing edges.
- A turbine as claimed in any one of the preceding claims, comprising a ring of turbine blades arranged in the annular path of a turbine working fluid, each blade being of at least approximately constant aerofoil cross-section from its root at the radially inner end to its tip at the radially outer end, and the blade being substantially symmetrically curved between the root and the tip so that the pressure face of the aerofoil blade is convex in the radial direction between root and tip.
- A turbine according to Claim 5, wherein the aerofoil sections at the root and tip of the blade are rotated in their own plane relative to the mid-height section by an angle within the range 5° ± 2°.
- A turbine according to Claim 6, wherein the said aerofoil sections are rotated in their own plane relative to the mid-height section by an angle within the range 5°± 1°
- A turbine according to any one of Claims 5 to 7, wherein the aerofoil sections of the blade lie on a parabolic curve between the root and the tip.
- A turbine according to any one of Claims 5 to 8, wherein the trailing edge of the blade is straight from root to tip and the convex curvature of the blade pressure face in the radial direction is achieved by rotational displacement of the aerofoil sections about the straight trailing edge.
- A turbine as claimed in any one of Claims 5 to 9, wherein the blades are fixed blades.
- A turbine as claimed in Claim 10, wherein the ratio of the throat between adjacent fixed blades to the pitch of the blades gives the sine of an outlet angle for the blades which is in the range 7° to 11° at the root of the blades.
- A turbine as claimed in Claim 11, wherein said outlet angle is in the range 8°to 10°.
- A turbine as claimed in Claim 11 or Claim 12, wherein the setting angle of the mid-height section of the fixed blades is such, in combination with the root outlet angle, as to provide a total passage throat area equal to that of a turbine having prismatic blades of the same stagger angle.
- A turbine as claimed in any of Claims 5 to 13, having a series of stages adapted for decreasing fluid density of the working fluid, wherein the outlet angle at the root of the blades is constant throughout the series of stages and the setting angle for the blade aerofoil sections at the mid-height of the blades is such as to maintain a predetermined throat area for the blades of each stage.
- A turbine as claimed in Claim 14, wherein said predetermined throat area is the throat area provided by prismatic blades in the corresponding stage of an otherwise similar conventional turbine.
- A turbine as claimed in any one of the preceding claims, wherein the turbine is a steam turbine.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB9417406A GB9417406D0 (en) | 1994-08-30 | 1994-08-30 | Turbine blade |
GB9417406 | 1994-08-30 | ||
EP95305720A EP0704602B1 (en) | 1994-08-30 | 1995-08-16 | Turbine blade |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP95305720A Division EP0704602B1 (en) | 1994-08-30 | 1995-08-16 | Turbine blade |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1046783A2 EP1046783A2 (en) | 2000-10-25 |
EP1046783A3 EP1046783A3 (en) | 2000-12-20 |
EP1046783B1 true EP1046783B1 (en) | 2006-03-15 |
Family
ID=10760549
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00116388A Expired - Lifetime EP1046783B1 (en) | 1994-08-30 | 1995-08-16 | Turbine blade units |
EP95305720A Expired - Lifetime EP0704602B1 (en) | 1994-08-30 | 1995-08-16 | Turbine blade |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP95305720A Expired - Lifetime EP0704602B1 (en) | 1994-08-30 | 1995-08-16 | Turbine blade |
Country Status (7)
Country | Link |
---|---|
US (2) | US5779443A (en) |
EP (2) | EP1046783B1 (en) |
JP (2) | JP3896169B2 (en) |
CN (2) | CN1272524C (en) |
DE (2) | DE69534860T2 (en) |
GB (2) | GB9417406D0 (en) |
ZA (1) | ZA956883B (en) |
Families Citing this family (67)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB9417406D0 (en) * | 1994-08-30 | 1994-10-19 | Gec Alsthom Ltd | Turbine blade |
DE19612396C2 (en) * | 1996-03-28 | 1998-02-05 | Univ Dresden Tech | Blade with differently designed profile cross sections |
EP0798447B1 (en) * | 1996-03-28 | 2001-09-05 | MTU Aero Engines GmbH | Turbomachine blade |
EP1012445B2 (en) * | 1997-09-08 | 2008-01-16 | Siemens Aktiengesellschaft | Blade for a turbo-machine |
DE69921320T2 (en) * | 1998-06-12 | 2005-10-27 | Ebara Corp. | TURBINENSTATORSCHAUFEL |
US6183192B1 (en) * | 1999-03-22 | 2001-02-06 | General Electric Company | Durable turbine nozzle |
US6419446B1 (en) * | 1999-08-05 | 2002-07-16 | United Technologies Corporation | Apparatus and method for inhibiting radial transfer of core gas flow within a core gas flow path of a gas turbine engine |
DE19941133C1 (en) * | 1999-08-30 | 2000-12-28 | Mtu Muenchen Gmbh | Blade crown ring for gas turbine aircraft engine has each blade provided with curved transition region between blade surface and blade platform fitting in opening in carrier band |
US6331100B1 (en) | 1999-12-06 | 2001-12-18 | General Electric Company | Doubled bowed compressor airfoil |
GB0003676D0 (en) * | 2000-02-17 | 2000-04-05 | Abb Alstom Power Nv | Aerofoils |
JP2002221006A (en) * | 2001-01-25 | 2002-08-09 | Ishikawajima Harima Heavy Ind Co Ltd | Throat area measurement method for turbine nozzle |
US6508630B2 (en) | 2001-03-30 | 2003-01-21 | General Electric Company | Twisted stator vane |
KR100587571B1 (en) * | 2001-10-10 | 2006-06-08 | 가부시끼가이샤 히다치 세이사꾸쇼 | Turbine blade |
GB2384276A (en) * | 2002-01-18 | 2003-07-23 | Alstom | Gas turbine low pressure stage |
JP4269723B2 (en) * | 2003-03-12 | 2009-05-27 | 株式会社Ihi | Turbine nozzle |
GB2407136B (en) * | 2003-10-15 | 2007-10-03 | Alstom | Turbine rotor blade for gas turbine engine |
US7175393B2 (en) * | 2004-03-31 | 2007-02-13 | Bharat Heavy Electricals Limited | Transonic blade profiles |
US7547186B2 (en) | 2004-09-28 | 2009-06-16 | Honeywell International Inc. | Nonlinearly stacked low noise turbofan stator |
GB0704426D0 (en) * | 2007-03-08 | 2007-04-18 | Rolls Royce Plc | Aerofoil members for a turbomachine |
JP4956277B2 (en) * | 2007-05-24 | 2012-06-20 | 株式会社東芝 | Nozzle cascade, rotor cascade, and axial turbine |
DE102008055824B4 (en) * | 2007-11-09 | 2016-08-11 | Alstom Technology Ltd. | steam turbine |
JP4929193B2 (en) * | 2008-01-21 | 2012-05-09 | 三菱重工業株式会社 | Turbine cascade endwall |
JP5291355B2 (en) * | 2008-02-12 | 2013-09-18 | 三菱重工業株式会社 | Turbine cascade endwall |
EP2133573B1 (en) * | 2008-06-13 | 2011-08-17 | Siemens Aktiengesellschaft | Vane or blade for an axial flow compressor |
GB0821429D0 (en) * | 2008-11-24 | 2008-12-31 | Rolls Royce Plc | A method for optimising the shape of an aerofoil |
US20110097205A1 (en) * | 2009-10-28 | 2011-04-28 | General Electric Company | Turbine airfoil-sidewall integration |
US8137062B2 (en) | 2010-05-11 | 2012-03-20 | General Electric Company | Turbomachine nozzle |
GB201011854D0 (en) * | 2010-07-14 | 2010-09-01 | Isis Innovation | Vane assembly for an axial flow turbine |
WO2012053024A1 (en) * | 2010-10-18 | 2012-04-26 | 株式会社 日立製作所 | Transonic blade |
US8523530B2 (en) * | 2010-12-21 | 2013-09-03 | Hamilton Sundstrand Corporation | Turbine rotor for air cycle machine |
EP2476862B1 (en) * | 2011-01-13 | 2013-11-20 | Alstom Technology Ltd | Vane for an axial flow turbomachine and corresponding turbomachine |
WO2012131905A1 (en) * | 2011-03-29 | 2012-10-04 | 株式会社日立製作所 | Turbine stator vane, steam turbine facilities using same, and turbine stator vane design method |
US8777564B2 (en) | 2011-05-17 | 2014-07-15 | General Electric Company | Hybrid flow blade design |
CN102305174B (en) * | 2011-07-04 | 2014-07-16 | 张向增 | Blade with constant cross section, forming method and horizontal axis wind turbine impeller comprising same |
US9255480B2 (en) * | 2011-10-28 | 2016-02-09 | General Electric Company | Turbine of a turbomachine |
US9157326B2 (en) | 2012-07-02 | 2015-10-13 | United Technologies Corporation | Airfoil for improved flow distribution with high radial offset |
EP2827003B1 (en) * | 2013-07-15 | 2019-04-10 | MTU Aero Engines GmbH | Gas turbine compressor guide vane assembly |
US20150110617A1 (en) * | 2013-10-23 | 2015-04-23 | General Electric Company | Turbine airfoil including tip fillet |
US10352180B2 (en) * | 2013-10-23 | 2019-07-16 | General Electric Company | Gas turbine nozzle trailing edge fillet |
WO2015175058A2 (en) * | 2014-02-19 | 2015-11-19 | United Technologies Corporation | Gas turbine engine airfoil |
EP2921647A1 (en) | 2014-03-20 | 2015-09-23 | Alstom Technology Ltd | Gas turbine blade comprising bended leading and trailing edges |
US10036400B2 (en) * | 2014-05-02 | 2018-07-31 | Regal Beloit America, Inc. | Centrifugal fan assembly and methods of assembling the same |
CN104047889B (en) * | 2014-06-09 | 2017-11-17 | 江苏大学 | A kind of method for eliminating axial-flow pump blade tip clearance interior angle whirlpool |
JP6468414B2 (en) * | 2014-08-12 | 2019-02-13 | 株式会社Ihi | Compressor vane, axial compressor, and gas turbine |
US10221708B2 (en) * | 2014-12-03 | 2019-03-05 | United Technologies Corporation | Tangential on-board injection vanes |
US10107108B2 (en) | 2015-04-29 | 2018-10-23 | General Electric Company | Rotor blade having a flared tip |
JP6421091B2 (en) * | 2015-07-30 | 2018-11-07 | 三菱日立パワーシステムズ株式会社 | Axial flow compressor, gas turbine including the same, and stationary blade of axial flow compressor |
ES2717801T3 (en) | 2015-10-26 | 2019-06-25 | MTU Aero Engines AG | Mobile praise |
US20170138202A1 (en) * | 2015-11-16 | 2017-05-18 | General Electric Company | Optimal lift designs for gas turbine engines |
GB2544735B (en) * | 2015-11-23 | 2018-02-07 | Rolls Royce Plc | Vanes of a gas turbine engine |
CN105604611A (en) * | 2016-03-03 | 2016-05-25 | 哈尔滨工程大学 | Variable-geometry turbine with strake wing structure of moving blade |
DE102016115868A1 (en) * | 2016-08-26 | 2018-03-01 | Rolls-Royce Deutschland Ltd & Co Kg | High-efficiency fluid flow machine |
US20190106989A1 (en) * | 2017-10-09 | 2019-04-11 | United Technologies Corporation | Gas turbine engine airfoil |
JP6982482B2 (en) * | 2017-12-11 | 2021-12-17 | 三菱パワー株式会社 | Variable vane and compressor |
US10808535B2 (en) * | 2018-09-27 | 2020-10-20 | General Electric Company | Blade structure for turbomachine |
CN109530768B (en) * | 2018-11-06 | 2020-03-17 | 中国航发贵州黎阳航空动力有限公司 | Machining method for blade tip edging thinning area |
JP7162514B2 (en) * | 2018-12-07 | 2022-10-28 | 三菱重工業株式会社 | Axial turbomachinery and its blades |
JP7406920B2 (en) * | 2019-03-20 | 2023-12-28 | 三菱重工業株式会社 | Turbine blades and gas turbines |
JP2020159911A (en) * | 2019-03-27 | 2020-10-01 | 三菱日立パワーシステムズ株式会社 | Gauge, method for measuring the same, method for evaluating accuracy of shape measurement machine, and method for correcting measurement data |
EP3816397B1 (en) * | 2019-10-31 | 2023-05-10 | General Electric Company | Controlled flow turbine blades |
DE102019220493A1 (en) * | 2019-12-20 | 2021-06-24 | MTU Aero Engines AG | Gas turbine blade |
IT202000005146A1 (en) | 2020-03-11 | 2021-09-11 | Ge Avio Srl | TURBINE ENGINE WITH AERODYNAMIC PROFILE HAVING HIGH ACCELERATION AND LOW VANE CURVE |
US11236628B1 (en) * | 2020-12-16 | 2022-02-01 | General Electric Company | Turbine nozzle airfoil profile |
US11459892B1 (en) * | 2021-04-30 | 2022-10-04 | General Electric Company | Compressor stator vane airfoils |
CN113237691B (en) * | 2021-05-08 | 2022-04-15 | 西安建筑科技大学 | Structural undisturbed soil sampling device and sampling method |
WO2022238770A1 (en) * | 2021-05-11 | 2022-11-17 | Ghalandari Mohammad | Blades of an axial turibine |
CN113279817B (en) * | 2021-06-08 | 2022-07-05 | 哈尔滨汽轮机厂有限责任公司 | Method for correcting influence of blade end rounding on flow |
Family Cites Families (35)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1553083A (en) * | 1924-05-06 | 1925-09-08 | Gen Electric | Elastic-fluid turbine |
GB534991A (en) * | 1939-01-18 | 1941-03-25 | British Thomson Houston Co Ltd | Improvements in and relating to methods of making elastic fluid turbine buckets |
US3714017A (en) * | 1967-10-12 | 1973-01-30 | Siemens Ag | Electrode device for electrochemically forming the plates of turbine rotors |
US3556675A (en) * | 1969-01-29 | 1971-01-19 | Gen Electric | Turbomachinery rotor with integral shroud |
US3837761A (en) * | 1971-08-20 | 1974-09-24 | Westinghouse Electric Corp | Guide vanes for supersonic turbine blades |
US3989406A (en) * | 1974-11-26 | 1976-11-02 | Bolt Beranek And Newman, Inc. | Method of and apparatus for preventing leading edge shocks and shock-related noise in transonic and supersonic rotor blades and the like |
US4131387A (en) * | 1976-02-27 | 1978-12-26 | General Electric Company | Curved blade turbomachinery noise reduction |
US4213736A (en) * | 1978-06-05 | 1980-07-22 | Innerspace Corporation | Turbomachinery and method of operation |
US4464094A (en) * | 1979-05-04 | 1984-08-07 | Trw Inc. | Turbine engine component and method of making the same |
JPS5718405A (en) * | 1980-07-07 | 1982-01-30 | Hitachi Ltd | Stage structure of turbine |
US4804311A (en) * | 1981-12-14 | 1989-02-14 | United Technologies Corporation | Transverse directional solidification of metal single crystal articles |
GB2129882B (en) * | 1982-11-10 | 1986-04-16 | Rolls Royce | Gas turbine stator vane |
FR2556409B1 (en) * | 1983-12-12 | 1991-07-12 | Gen Electric | IMPROVED BLADE FOR A GAS TURBINE ENGINE AND MANUFACTURING METHOD |
AU592756B2 (en) * | 1984-06-18 | 1990-01-25 | Mitsubishi Jukogyo Kabushiki Kaisha | Scroll type fluid machine and method for forming scroll members used therein |
GB2164098B (en) * | 1984-09-07 | 1988-12-07 | Rolls Royce | Improvements in or relating to aerofoil section members for turbine engines |
DE3514122A1 (en) * | 1985-04-19 | 1986-10-23 | MAN Gutehoffnungshütte GmbH, 4200 Oberhausen | METHOD FOR PRODUCING A GUIDE BLADE FOR A TURBINE OR COMPRESSOR LEAD, AND GUIDE BLADE PRODUCED BY THE METHOD |
GB2177163B (en) * | 1985-06-28 | 1988-12-07 | Rolls Royce | Improvements in or relating to aerofoil section members for gas turbine engines |
US4741667A (en) * | 1986-05-28 | 1988-05-03 | United Technologies Corporation | Stator vane |
FR2603953B1 (en) * | 1986-09-12 | 1991-02-22 | Peugeot Aciers Et Outillage | PROPELLER BLADE AND ITS APPLICATION TO MOTOR FANS |
US4826400A (en) * | 1986-12-29 | 1989-05-02 | General Electric Company | Curvilinear turbine airfoil |
FR2610673B1 (en) * | 1987-02-05 | 1991-03-15 | Snecma | MULTIFLUX TURBOREACTOR WITH EXTERNAL CROWN OF FREQUENCY BLOWER RECTIFIER ON THE CRANKCASE |
FR2619330B1 (en) * | 1987-08-12 | 1994-03-11 | Snecma | PROCESS FOR PRODUCING STATOR STAGES OF COMPRESSOR OR TURBINE, BLADES AND GRIDS OF BLADES THUS OBTAINED |
GB2219882B (en) * | 1988-06-20 | 1992-03-11 | Wang Hsug Fang | Signal device for pneumatic tires |
DE3842710C1 (en) * | 1988-12-19 | 1989-08-03 | Mtu Muenchen Gmbh | |
US5088892A (en) * | 1990-02-07 | 1992-02-18 | United Technologies Corporation | Bowed airfoil for the compression section of a rotary machine |
JP2753382B2 (en) * | 1990-09-17 | 1998-05-20 | 株式会社日立製作所 | Axial flow turbine vane device and axial flow turbine |
GB2253443A (en) * | 1991-03-05 | 1992-09-09 | Rolls Royce Plc | Gas turbine nozzle guide vane arrangement |
GB9119846D0 (en) * | 1991-09-17 | 1991-10-30 | Rolls Royce Plc | Aerofoil members for gas turbine engines and method of making the same |
GB9210421D0 (en) * | 1992-05-15 | 1992-07-01 | Gec Alsthom Ltd | Turbine blade assembly |
GB2267736B (en) * | 1992-06-09 | 1995-08-09 | Gen Electric | Segmented turbine flowpath assembly |
DE4228879A1 (en) * | 1992-08-29 | 1994-03-03 | Asea Brown Boveri | Turbine with axial flow |
JP3132944B2 (en) * | 1993-03-17 | 2001-02-05 | 三菱重工業株式会社 | Three-dimensional design turbine blade |
US5326221A (en) * | 1993-08-27 | 1994-07-05 | General Electric Company | Over-cambered stage design for steam turbines |
US5352092A (en) * | 1993-11-24 | 1994-10-04 | Westinghouse Electric Corporation | Light weight steam turbine blade |
GB9417406D0 (en) * | 1994-08-30 | 1994-10-19 | Gec Alsthom Ltd | Turbine blade |
-
1994
- 1994-08-30 GB GB9417406A patent/GB9417406D0/en active Pending
-
1995
- 1995-08-11 GB GB9516493A patent/GB2295860B/en not_active Expired - Fee Related
- 1995-08-16 EP EP00116388A patent/EP1046783B1/en not_active Expired - Lifetime
- 1995-08-16 DE DE69534860T patent/DE69534860T2/en not_active Expired - Lifetime
- 1995-08-16 DE DE69520061T patent/DE69520061T2/en not_active Expired - Lifetime
- 1995-08-16 EP EP95305720A patent/EP0704602B1/en not_active Expired - Lifetime
- 1995-08-17 ZA ZA956883A patent/ZA956883B/en unknown
- 1995-08-23 JP JP23773895A patent/JP3896169B2/en not_active Expired - Lifetime
- 1995-08-30 CN CNB01108894XA patent/CN1272524C/en not_active Expired - Lifetime
- 1995-08-30 CN CN95116394A patent/CN1071837C/en not_active Expired - Lifetime
-
1997
- 1997-08-22 US US08/918,709 patent/US5779443A/en not_active Expired - Lifetime
-
1998
- 1998-02-27 US US09/032,515 patent/US5906474A/en not_active Expired - Lifetime
-
2005
- 2005-06-13 JP JP2005172719A patent/JP2005320973A/en active Pending
Also Published As
Publication number | Publication date |
---|---|
CN1126796A (en) | 1996-07-17 |
EP0704602A2 (en) | 1996-04-03 |
DE69520061T2 (en) | 2001-08-23 |
CN1272524C (en) | 2006-08-30 |
JP3896169B2 (en) | 2007-03-22 |
US5906474A (en) | 1999-05-25 |
CN1071837C (en) | 2001-09-26 |
DE69520061D1 (en) | 2001-03-15 |
DE69534860D1 (en) | 2006-05-11 |
EP1046783A3 (en) | 2000-12-20 |
DE69534860T2 (en) | 2006-10-12 |
JPH0874502A (en) | 1996-03-19 |
GB2295860B (en) | 1998-12-16 |
ZA956883B (en) | 1996-03-25 |
GB9516493D0 (en) | 1995-10-11 |
EP0704602B1 (en) | 2001-02-07 |
US5779443A (en) | 1998-07-14 |
JP2005320973A (en) | 2005-11-17 |
EP0704602A3 (en) | 1996-07-10 |
EP1046783A2 (en) | 2000-10-25 |
CN1330209A (en) | 2002-01-09 |
GB2295860A (en) | 1996-06-12 |
GB9417406D0 (en) | 1994-10-19 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1046783B1 (en) | Turbine blade units | |
US6709233B2 (en) | Aerofoil for an axial flow turbomachine | |
KR100566759B1 (en) | Turbine nozzle vane | |
EP0997612B1 (en) | A circumferential row of aerofoil members of a turbomachine | |
US5221181A (en) | Stationary turbine blade having diaphragm construction | |
EP0985801B1 (en) | Blade configuration for steam turbine | |
US5292230A (en) | Curvature steam turbine vane airfoil | |
US20110164970A1 (en) | Stator blade for a turbomachine, especially a stream turbine | |
US5035578A (en) | Blading for reaction turbine blade row | |
JPS5990797A (en) | Centrifugal compressor and compression method | |
CA2091698A1 (en) | Controlled reaction l-2r steam turbine blade | |
EP0775249A1 (en) | Flow directing assembly for the compression section of a rotary machine | |
JPH04262002A (en) | Stationary blade structure for steam turbine | |
EP1260674B1 (en) | Turbine blade and turbine | |
US7794202B2 (en) | Turbine blade | |
US2830753A (en) | Axial flow compressors with circular arc blades | |
US6109869A (en) | Steam turbine nozzle trailing edge modification for improved stage performance | |
JPH04219403A (en) | Turbine blade | |
JPS6128801B2 (en) | ||
US4137709A (en) | Turbomachinery and method of operation | |
JPH03189304A (en) | Stationary blade for axial-flow fluid machinery | |
GB2323896A (en) | Turbine blade interface with end-block | |
JPH0689651B2 (en) | Axial flow fluid machine | |
JPH03267506A (en) | Stationary blade of axial flow turbine | |
JP2000104501A (en) | Turbine moving blade, gas turbine and steam turbine |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AC | Divisional application: reference to earlier application |
Ref document number: 704602 Country of ref document: EP |
|
AK | Designated contracting states |
Kind code of ref document: A2 Designated state(s): BE CH DE DK FR LI NL |
|
PUAL | Search report despatched |
Free format text: ORIGINAL CODE: 0009013 |
|
AK | Designated contracting states |
Kind code of ref document: A3 Designated state(s): BE CH DE DK FR LI NL |
|
RIC1 | Information provided on ipc code assigned before grant |
Free format text: 7F 01D 5/14 A, 7F 01D 9/02 B |
|
17P | Request for examination filed |
Effective date: 20010202 |
|
AKX | Designation fees paid |
Free format text: BE CH DE DK FR LI NL |
|
17Q | First examination report despatched |
Effective date: 20040803 |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AC | Divisional application: reference to earlier application |
Ref document number: 0704602 Country of ref document: EP Kind code of ref document: P |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): DE FR |
|
RAP2 | Party data changed (patent owner data changed or rights of a patent transferred) |
Owner name: ALSTOM TECHNOLOGY LTD |
|
REF | Corresponds to: |
Ref document number: 69534860 Country of ref document: DE Date of ref document: 20060511 Kind code of ref document: P |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: TP Ref country code: FR Ref legal event code: CA Ref country code: FR Ref legal event code: CD |
|
ET | Fr: translation filed | ||
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed |
Effective date: 20061218 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: ST Effective date: 20110502 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20100831 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20090914 Year of fee payment: 15 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20140901 Year of fee payment: 20 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R071 Ref document number: 69534860 Country of ref document: DE |